Mathematical modeling of the cooling system for a 5.5 MW gas turbine engine

The paper describes an approach to the thermohydraulic calculation of the cooling system of a single-shaft gas turbine engine (GTE). The calculation is based on the development of a detailed one-dimensional model of the channel geometry of the cooling air supply system to the main cooled elements of a gas turbine engine. The calculation in the mathematical model is based on Kirchhoff's laws 1 and 2, with the identification of a minimum spanning tree in the form of a graph in which branches and nodes form a hydraulic network. The arrangements of cooling air supply from the axial compressor to the journal bearing, thrust bearings, and stator and rotor of the turbine are considered. A detailed one-dimensional model of the channels of the cooling air supply system has been developed, including one-dimensional models of the cooling air channels in the nozzle and rotor blades of the turbine. As a result, the distribution of pressures and flow rates in the channels of the cooling system was obtained. One-dimensional computational models of the cooling channels of the nozzle and rotor blades of the turbine are verified based on cold flow tests on a flow capacity test bench. One-dimensional (at the mean diameter) and three-dimensional (CFD) gas-dynamic calculations of the turbine were performed to determine the distribution of gas flow parameters across the turbine blade rows. The results of these calculations were used as boundary conditions for the mathematical model of the cooling system channels. A thermohydraulic calculation of the regenerative cooling system of the combustor liner in a one-dimensional formulation was also performed. As a result of the calculation, the total pressure losses and wall temperature distribution of the liner were determined along the cooling air flow.

Based on the developed one-dimensional model of the gas turbine engine cooling system, the hydrodynamic characteristics were determined; the velocities, flow rates, pressures and temperatures of the coolant in all channels of the cooling passage were determined.

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